Aeroplane



J. C. DAYNIX Oct. 20, 1 925" AEROPLANE 4 Sheets-Sheet 1 File Aug. 7, 1924 Oct. 20,1925- J. c. DAYNIX AERDPLANE 4 Sheets-Sheet 2 Filed Aug. '7 1924 J. C.v DAYNIX Oct. 20, 1925.

AEROPLANE Filed Aug. 7, 1924 J. C. DAYNIX AEROPLANE 4 Sheets-Sheet 4- Filed Aug. 7,

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AEROPLANE.

Application filed August 7, 1924. Serial No. 730,586.

To 1/]? whom it may concern lie it known that l. JOHN DAYXI'... a citizen of the United States. residing at Philadelphia. in the county of Philadelphia and idtate of Pennsylvania. have invented certain new and useful ln'iprovemcnts in Aeroplanes. of which the following is a specification.

This invention relates to aircraft and it has more particular reference to that type commonly designated heavier than air flyinn nnurhines. the primary object being to provide an aeroplane having an adequate maintenance surface with a relatively decreased wing spread.

.inother object of this invention is to produce an aeroplane which will automatically control and utilize the air to best ad vantage during flight. instead of said aeroplane being. as now generally obtains. more or controlled thereby.

further object is to furnish an aeroplane characterized by means productive of vacuum waves and buoyancy currents so directed compress and bank air currents longitudi nallv of the machine with incidental increased lmoyancy. and a reduction to the minimum of adverse effects liable to be set 1p when encmintering cross currents; to pro vid a flying machine which can effect an aquatic landing with perfect. ease" and be easilv navigated to suitable anchorage; to autoii'iatically stabilize the machine with maintenance on an even heel; and to produce a dying machine capable of great. carrying capacity without being cumbersome and ungainly to manoeuvre.

My invention furtherembodies all of the foregoing: and other novel objects and advantao'es hereinafter referred to; or which will become apparent from the following detailed description of one practical form thereof. chosen from many others as well adapted to clearly exemplify and explain its novel characteristics; while the scope of said invention 'is succinctly defined by the subjoined claims.

In order that those skilled in the art may fully understand this invention I have more or less conventionally shown the same in the accompanying sheets of drawings, with omission of such structural details. as might be conducive to complex illustration. whereby the novel features will be better appreciated in correct perspective. In the several views of the drawings, like reference indicies are employed to designate the same or corresponding parts.

Figure 1. is a. perspective view of my novel aircraft looking angularly astern.

l igure 2 is a similar view looking ahead.

Figure 3 is a longitudinal vertical section.

Figure 4 is a top plan view.

Figure 5 is a front endele-vation.

Figure 6 is a somewhat enlarged detail view of the forward motor and associated controls.

Figure 7 is a similar detail View of the rear motor and marine propulsion mocha" nism.

Figure 8 is a detail view of an automatic stabilizer device hereinafter more fully explained; and

Figure 9 is a diagrammatic plan of the rudder control.

Referring more in detail to the drawings itwill be seen that my novel aircraft comprises a fuselage 9 of approximately-- though not cssentially-rectangular or other tubular cross section, divided at intervals by partitions (not shown) to provide navigation, passenger, freight and other accommodation, as well as the necessary quarters for the crew and dining facilities. In addition to the foregoing a medial section of the fuselage 9 is set apart for the housing of a stabilizer instrumentality. comprehensively designated by the numeral 10, Figures 3 and 8. the same being hereinafter fully described. The fuselage 9. as will be best seen from Figures 1. 2 and 4. is suitably nosed at its fore-and-aft ends 11, 12, respectively, While it surniounts a longitudinal tank or tanks 13. subdivided to afford storage for fuel, oil

and other accessories, as well as providing.

adequate space to accommodate mail, baggage and other freight to be transported. Th tank. OI tanks 13, in turn is mounted upon a pair of longitudinally disposed and spaced pontoons 14:, 14, affording therebetween a cambered tunnel. 15 co-extensive and aligned with the longitudinal median line of the aircraft for a purpose later on fully set forth. v

Thesepontoons 14, 14, it will be readily understood are preferably shaped in their sub-portions to simulate hulls effective for easy aquatic launching and navigation, while the cambered superstructure intermediate the same affords a rigid keel or back bone for the entire craft, This feature I have found of prime importance in that it serves a dual purpose; to-wit, supports the dead weight in a buoyant manner, as well .as to all practical intents eliminating vibration during navigation. These pontoons 14, 1 1, may also be utilized as storage for compressed air or a non-inflammable gas, whereby the craft is rendered much more buoyant in flight, while they also provide housing for thelanding wheels 16, that are mounted on transverse shafts 17, journaled in suitable bearings therein. At this juncture it is well to point out that the landing wheels 16 are omitted in Figures 1 and 2, as well as certain other mechanisms and instrumentalities later on particularly detailed in connection with other views, in order not to conflict with the planal structure and cause complex illustration.

Referring again to the fuselage 9 and as best shown by Figures 1, 2, 3 and 5, it will be seen that the floor or deck thereof is coextensive and colanai with a main plane or aerofoil 18, the ongitudinal edges whereof are downwardly curved or rolled at 19 for a purpose later on explained. Mounted in superposed, but slightly declined relation to the plane or aerofoil 18, and extending foreand-aft of the upper part of roof 20 of the fuselage 9, are what may be conveniently designated longitudinal sustaining planes 21, 21, braced at intervals by stanchions-mot shownand having theirlongitudinal outer edges downwardly cambered or rolled at 22 for a similar purpose to that referred to in connection with the main lane or aerofoil 18. In connection with this part of my invention, it is well to here point out when statin that the sustaining'planes 21, 21 are slightly declined it is to be clearly unden stood that assuming the main plane or aerofoil 18 is disposed horizontal, the vertical altitude between said sustaining planes at the front end. of the machine is somewhat greater than that at the rear. Sr, in other words, the sustaining planes 21, 21 have a slight longitudinal declination relative to the main plane or aerofoil 18, so that when the machine is in flight parallel columns of air are slightly compressed longitudinally at each side of the fuselage 9 thereby assisting the production of a vertical suction in an upward direction, as well as materially aiding stability by establishing-buoyancy currents at each side of the machine. In connection with the foregoing features attention is also directed to the longitudinal and downwardly rolled edges 22 whereby the longitudinal air currents intervening the main plane or aerofoil 18 and the sustaining planes 21, 21, according to its density or rarity while slightly compressed are also inwardly banked relative to the fuselage 9. This simultaneous compressive and banking of the longitudinally aligned buoyancy currents, I have found greatly increases the general stability of'the machine, while countering adverse cross currents having a tendency to disturb equilibrium ordeviation from an even keel.

In combination with the sustaining wing planes 21, 21, just described, as shown by Figures 1 and 2', or in lieu thereof, as illustrated in Figures 3, 4 and 5, I fit my novel flying machine with a series of rearwardly stepped and slightly declined sustaining wing planes 23. 24, 25' similarly disposed relative to the main plane oraerofoil 18 as hereinbefore set forth. These sustaining wing planes 23, 24, 25 are, however, each fitted with a forwardly directed arcuate nose portion 26in' the art commonly designated bull-noses-hinged transversely of the machine at 27, and all capable of simultaneous and uniform adjustment, whereby the angular deflection of the buoyancy currents directed below said wing planes may be varied at will. A convenient means to accomplish this uniform adjustment of the nose portions 26, is more or less diagrammatically shown in Figure 3, and it comprisesia series of bell cranks 28, fulcrumed at 29 to the fuselage 9, and connected to said nose portions by pivotal links 30. These bell cranks 28 are in turn coordinated for synchronous move ment by connecting rods 31 under control of a hand or power control 32, and associated locking quadrant in the pilot house at the fore part of the fuselage. In Figures 1 and 2, it will be observable that the forward wing planes 23, 24 are to all practical in tent dispensed with while the wing planes 25 are considerably shorter than as indicated in Figure 3, it being obvious such arrangement is consequent upon the close relation of the wing planes 21 to thenose portions 26. Furthermore, I desire at this juncture to lay particular stress on the purpose of the sustaining planes 23, 24 and 25 with their associated nose portions 26; namely, the establishment of vacuum waves longitudinally of the 11 perregions of the machine which constanty create and maintain a vertical suction during flight. This phase of my invention is of primary importance as l have found that the buoyancy and carrying capacity of the machine is very i'naterially augmented thereby.

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In conjunction with the means just described for maintaining vacuum waves longitudinally of the machine, I provide a longitudinal tunnel or tube 34, (JO-OXtQHSlVQ and axially aligned above the roof '29of the fuselage 9, said tube being of any convenient cross section and graduallythough not essentially so-decreased in area slightly rearwards of the machine. In the cinbodiment of my invention, shown by Figures 1 and 2, it will be observed that this tunnel or tube 3 f is interrupted transversely at 3-1" to accommodate the adjustable noses 26, so that each said nose portion is functional to direct a column of air thereinto with more or less velocity and compressive action whereby a powerful bouyancy current. is continuously maintained co-axially and longitudinally central above the fuselage roof 20 for a very obvious purpose.

Somewhat similarly I provide longitudinally at each side of the fuselage 9 openended tubes 35, 35 (one at each side thereof) and conveniently rectangular in cross section. These tubes 35, 35, as best understood from Figure l, are rearwardly declined for the major portion of their length and thereafter diverted at 36 upwardly in so far as their upper walls are concerned, and said rear portions are fitted with adjustable shutters 37- -Figures 1 and 5- functional as choke devices. It will, of course be well understood that these shutters 3 7 are coordinated and normally re pose snugly against the underside of the upwardly inclined'portions 36, so as to offer no resistance to the free fiow'of buoyancy currents through the tubes 35, 35; but that appropriate excentric mechanism indicated at 38, and operable from the pilot house is provided, whereby they may be downwardliy swung to more or less close the exit en tilt of said tubes. When so declined the shutters 37 will compress the buoyancy currents flowing through the tubes 35, 35, such as when effecting a landing, whereby an effective retarding or braking means is supplied.

In like manner, though not essentially so, the longitudinal tank or tanks 13 may be provided with supplemental buoyancy cur rent tubes 39, 39 of similar section and declination rearwardly of the machine, but minus any choke shutters, whereby it will be readily understood that the general stability of the machine is safeguarded and the buoyancy capacity increased to the maximum.

Stabilizer wings 40, 41, are fitted at each side of the fuselage and fore-and-aft thereof respectively, said wings being coordinated with and independently operable of or automatically controlled by the stabilizer device 10, hereinbefore referred to. This stablizer device 10 comprises a pendulum chamber 42, universally suspended at 43 and having suficient cubic capacity to afford storage for Figure 3 nected to a hand or power control 52, af-' forded bearing at 53 in the pilot house, as will bereadilyunderstood without further explanation. Connecting with the bearers 48 aforesaid is a convergent toggle linkage 54, having suitable vertical guidance and connected by a short link 55 with one arm of a bell-crank 56, fulcrumed at 57, to a lateral arm 58, on the rigid post 44; the other arm of said bell-crank being coordinated by a rod 59 to a manual or power control and associated lock quadrant-comprehensively designated 60.

Elevating rudders 61, 61, are fitted to the main plane or aerofoil 1.8, and are movable through the medium of rocker arms 62 coordinated by an appropriate connection 63 with a control lever 64, in the, well known way; hence a more elaborate detailed description thereof is omitted.

' In addition to the foregoing instrumentalities for ensuring perfect stability and control of the machine in flight, and by way of clarifying a distinction existent in the stabilizing means, it is noteworthy that when the several parts occupy the positions shown in Figure 8 the aviator or pilot can freely manipulate the stabilizer wings 41' from the control 52. @n the other hand, by elevating the bearers 48 until they are on a dead level with the bearing pivot 45 by manipulating the control 60, or as indicated by the dot and-dash line shown across Figure 8, the stabilizer 10 as a unit will become automatic. ally effective and function to maintain pen fect equilibrium during flight, as will be readily understood by those conversant with the art.

Thesteering rudder 65 is pivotally supor tube 34. Forwardly extended from one of the 'crossed rod or cable pivotal connections to the arms 72, is a rod 76 coordinated with a control lever 77, whereby the rudders 67, 74 are movable in reverse relation, and it will be readily understood that when said rudders are in neutral position, a column of slightly compressed air will be directed longitudinally rearwards of the upper surface of the machine that tends to substantially increase the vacuum suction essential to perfect buoyancy of heavier than air machines.

The motors 78, 78, for my improved flying machine arepreferably disposed fore and aft thereof in direct alignment with the longitudinal axis, and they are mounted securely under the main plane or aerofoil 18 above the cambered tunnel 15 whereby a firm and stable base is afforded therefor. Furthermore, by locating the motors 7 8, 78, as just set forth, it will be clear that vibratory disturbance inherent thereto is concentrated at the most invulnerable part of the machine, whereby the factor of safety in general is very materially increased. Incidentally it is to be remarked that the fore and aft propellers 79, 80, respectively, are draught and drive propellers whereby maximum speed in flight is ensured. Again the motors 78, 78, are, or'may be, of any approved type, it being understood that the showing in Figures land 2 is purely diagrammatic and entirely disproportionate in so far as capacity and sizeis concerned; the drawings having been made from photos of an accurately scaled model fitted with electric motors to test its behaviour in flight, and accordingly many times too large when the machine is considered from a full-size viewpoint. These motors 7 8, 78' are coordinated or clutched together to operate what may be broadly termed composite launching and aquatic propelling means. To thisend the power shafts 81, 82 of the motors 78, 78 are inwardly extended and journaled in bearings 83, said shafts being fitted with feathered clutch members 84, connected for simultaneous movement, through the medium of a longitudinal shifter rod 85, having forked engagement therewith. This shifter rod 85 is under the control of a lever 86 and associated lock quadrant 87 of any approved t e.

fts best shown by Figure 6, the forward motor 78 and associated clutch 84 is adapted to operate a bevel couple 88 in turn serving to rotate a vertical shaft 89, and through a second bevel drive 90, revolve the shaft 17 on which the forward landing wheels 16 are mounted. Similarly the rear or after motor 7 8 and associated clutch 84 is adapted to couple a bevel drive 91 operative to adapted to progress the machine when navigated in water or making a forced landing thereon. Incidentally, it may be mentioned that the peaks of the pontoons 14 are given suitable stream lines and appropriate rake, to facilitate easy marine navigation while the stems are butted, as best indicated in Figure. 3 to afford proper bearing for the propellers 95 Associated in a machine constructed and arranged for aerial and aquatic propulsion as described and shown, I may provide a sub-plane for side wings 96, 96, eo-extensivo with the top of the pontoons 14, 14, and having their longitudinal edges downwardly rolled at 97, and said plane or wingsmay be braced to the main plane or aerofoil' 18 by stanchions 98 or appropriate guys. The object and function of the sub-plane or wings 96, 96 is in a measure self-evident, but it may be briefly stated that it serves a dual purpose; namely, when the machine is in aerial flight it materially increases the sustaining power while when said machine is being navigated on water it augments the buoyancy by. banking air thereunder; To a similar degree the arched tunnel 15 compresses a column of air therein when the machine is on water, while when in aerial flight, consequent upon the specific position ing of the draught and drive propellers 79, 80, it will be readily appreciated that a buoyancy current is directly trained therethrough with obviously added flight efficiency, as well as in a sense lending compressive support co-extensive with the backbone or keel of the machine.

In addition to all the foregoing instrumentalities and means for ensuring perfect buoyancy and automatic control, I may provide the sustaining planes 23, 24, 25 on their upper surfaces with longitudinally directed T-section suction devices or rigid ailerons 99, Figures 4 and 5; the horizontal surfaces whereof are provided with perforations 100 that may be fitted with downwardly closing non-return valves whereby an added elevating impetus is ensured, as will be apparent to any one in the least acquainted with aerodynamics. It is also to be remarked that the horizontal portions of the suction devices 99 are preferably longitudinally cambered, as shown clearly in Figure 5, to more effectively trap and bank the suction currents.

From the foregoing description and on examination of the drawings it is thought that the inherent advantages and manner of manipulating, controlling and navigating my novel flying machine will be fully understood without repetitive description. Furthermore, while I have detailed a particular construction, combination and aggroupment of the several features involved, it is to be distinctly understood this specification includes Within its purview diversillU lid

reenter fied variations and modifications too numerous to enumerate. Accordin ly the. right is hereby reserved to include al such reasonable and other detail changes that fairly come within the scope of the appended claims.

Finally, it will be quite clear from the foregoing that a flying machine embodying the structural features set forth, includes an adequate sustaining area; is of maximum stability and buoyancy; while the vacuum waves and buoyancy currents are so directed and correlated as'to ensure absolute safety at all times, no matter what the flight conditions may be; c

Having described my invention what I claim is 1. A flying machine including a main aerofoil with the major dimension lengthwise ar d superposed vacuum Wave producing minor planes havin a rearward decl nation, and provided w1th adjustable noses.

A flying machine including a main aeroioil with the major dimension length wise, and superposed vacuum'waveproducing minor planes having a rearward declination, and adjustable arcuate section noses.

3. A flying machine including a main aercfoil with the major dimension len hwise, and superposed vacuum wave pro ucing minor planes having a rearward declination, and coordinated hinged bull noses.

l. A. flying machine including a main and superposed sustaining wing planes with the major dimension lengthwise and adjustable vacuum wave producing means associated above the wing planes.

5. A flying machine including a main and superposed sustaining wing planes with the major dimension lengthwise and coordinated adjustable laterally disposed arcuate means having capacity to produce vacuum waves,

6. it flying machine including a main aeroioil with the major dimension lengthwise of said machine, adjustable superposed Y vacuum wave producing lateral planes, a

buoyancy current passage co-entensive with the machine intersected by the lateral planes, and a sub-plane with associated pontoonsu ii machine including a main aeroioil with the major dimension length wise oi said'inachine, adjustable superposed vacuum wave producing lateral planes, a buoyancy current passage coextensive with the machine intersected by the lateral planes, and a sub-plane with underlying pontoons affording an arched keel for the purposespecified.

8. A flying machine including a main aero'loil with the major dimension lengthwise of said machine, superposed adjustable vacuum wave producing lateral planes with an associated buoyancy current passage, and suction devices mounted above the lateral planes.

9, A dying machine including a main aero foilwith the major dimension lengthwise at said machine, superposed adjustable vacu.

um wave producing lateral planes with an associated buoyancy current passage, and "if-section suction devices mounted above the lateral planes.

10. A flying machine including a main vacuum Wave producing lateral planes with an associated buoyancy current passage, and suction devices mounted above the lateral planes, said main and lateral planes as well as the suction devices having the longitudinlally directed edges thereof downwardly rol ed.

12. A flying machine including main supporting plane with the major dimension lengthwise thereof, a fuselage and sun mounted coextensive buoyancy current tube, laterally directed rearwardly declined wing planes adjacent the top of the fuses lage and air tight pontoons below the ma chine atlording an arched l;

13. A dying machine incliding a main supporting plane with the major dimension lengthwise thereof, a fuselage and surmounted co-extensive buoyancy current tube, laterally directed rearwardly declined wing planes having adjustable noses inter secting the buoyancy tube, and airtight pontoons below the machine affording an arched keel.

it. flying machine including a main supporting plane witl the major dimension lengthwise th of, a fuselage and sur mounted. co-eitcnsive buoyancy tube, laterally" directed. rearwardly dec lapping wing havi hate noses buoyancy tube, id

the fuselage an i A.

15. A flying machine having a main aero foil with the major dimension lengthwise thereof, and superposed vacuum wave pro ducing laterally directed minor planes, said minor planes slightly overlapping each other at the adjacent ends. 7

16. A. flying machine having a main aerofoil with the major dimension lengthwise thereof, and superposed vacuum wave producinglaterally directed and rearwardly declined minor lanes, said minor planes slightly overlapping each other at the adjacent ends.

17. A flying machine having a main aeroloil with the major dimension lengthwise Ell current a V teens below 3) llld lll l'lt Ell , ally thereof, and superposed vacuumwave procoordinate adjustable shutters for the purducing laterally directed and rearwardly pose specified. V declined minor planes, said minor planes 23. A flying machine including a' main slightly overlapping each other at the adj aaerofoil with the major dimension lengthwise cent ends, and having longitudinally dithereof, a fuselage and surmounted co-exrected suction devices on their upper faces. tensive buoyancy current tube, laterally di- 18. flylng machine including a main rected rearwardly declined wing planes havaerofoil with the major dimension lengthing coordinated adjustable nose portions ad wlse thereof, a fuselage and surmounted coja nt the top of th fuselage, a sub-plane extensive buoyancy current tube, laterally and parallel airtight pontoons below the directed rearwardly declined wing planes fuselage, a supplemental buoyancy current having ad ust-able noses adjacent the top Of tube at each side of the fuselage and longithe fuselage, parallel airtight pontoons betudinal thereof, landing wheels and marine low the fuselage affording an arched keel, propellers associated with the pontoons, and and a supplemental buoyancy current tube means whereby said wheels and propellers at-each side of the fuselage. may be operated to facilitate an easy ascent 19. A flying machine including a main and effect hydronavigation respectively. aerofoil with the major dimension length- 24 A flying machine including a main wise thereof, a fuselage and surmounted aerofoil with the major dimension lengthwise co-extenslve buoyancy current tube, late-rthereof, a fuselage and surmounted co-exdirected rearwardly declined wing tensive buoyancy current tube, laterally diplanes having adjustable noses adjacent the rected 'rearwardly declined wing planes havtop of the fuselage, parallel airtight poning coordinated adjustable nose portions adtoons below the fuselage aiiording an arched jacent the top of the fuselage, a sub-plane keel, and a supplemental buoyancy current and parallel airtight pontoons below the tube at each side of the fuselage, said supfuselage, a supplemental buoyancy current plemental tubes being fitted with coorditube at each side of the fuselage and longinated adjustable shutters for the purpose tudinal thereof, lateral stabilizer wings for specified. the machine, and means coordinating de- 20. A flying machine including a main fiection of said wings to assist ascent and aerofoil with the major dimension lengthlandin wise thereof, a fuselage and surmounted 25, co-extensive buoyancy current tube, lateraerofoil with the majordii'nension lengthwise ally directed rearwardly declined wing tliereof, a fuselage and surmounted co-explanes having adjustable noses adjacent the tensive buoyancy current tube, laterally ditop of the fuselage, a sub-plane below the'rected rearwardly'declined wing planes havfuselage having parallel airtight pontoons ing coordinated adjustable nose portions thereunder affording an arched keel, and a ad acent the top of the fuselage, a sub-plane supplemental buoyancy current tube at each and parallel airtight po-ntoons below the side of said fuselage. fuselage, a supplemental buoyancy current 21. A flying machine including a main tube at each side of the fuselage and longiaerofoil with the major dimension lengthtudinal thereof, lateral stabilizer wings for wise thereof, a fuselage and surmounted the machine and a coordinated stabilizing deco-extensive buoyancy current tube, latervice whereby said wings may be automatially directed rearwardly declined wing cally controlled during flight to maintain planes having adjustable noses: adjacent the the machine in equilibrium. top of the fuselage, a sub-plane below the 26. A flying machine includ ng a main fuselage having parallel airti 'ht pontoons aerofoil with the major dimension lengththereunder affording an arched keel, and a wise thereof,a fuselage and surmounted c0- su plemental buoyancy current tube at each extensive buoyancy current tube, laterally si e of said fuselage, the supplemental tubes directed rearwardly declined wing planes having coordinate adjustable shuttersfor having coordinated adjustable nose portions the purpose specified. adjacent the top of the fuselage, a sub-plane 22A flying machine including a main and parallel alrtight pontoons below the aerofoil with the major dimension lengthfuselage, a supplemental buoyancy current wise thereof, a fuselage and surmounted tube at each side of the fuselage and longico-extensive buoyancy current tube, latertudinal thereof, later-a1 stabilizer wings for ally directed rearwardly declined wing the machine, a coordinated stabilizing device planes having adjustable noses adjacent the whereby said win -s may be automatically top of the fuselage, storage capacity below controlled during ight to maintain the matthe fuselage having co-extensive buoyancy chine in equilibrium, and independent'optubes, a sub-plane and parallel airtight poncrating mechanism for eii'ecting manual contoons thereunder affording an arched keel, trol of the stabilizing wings. and a supplemental'buoyancy' current pas- 27. A flying machine including a main sage at each side of the fuselage fitted with aerofoil with the major dimension lengthg flying machine including a main wise thereof, a fuselage and surrounded coextensive buoyancy current tube, laterally directed rearwardly declined wing planes having coordinated adjustable nose portions adjacent the top of the fuselage, a sub-plane and parallel airtight pontoons below the fuselage, a supplemental buoyancy current tube at each side of the fuselage and longitudinal thereof, elevating rudders on the main aerofoil, and means whereby said elerating rudders are simultaneously operated.

'28. A flying machine including a main aerofoil with the major dimension lengthwise thereof, a fuselage and surmounted co-' extensive buoyancy current tube, laterally directed rearwardly declined wing planes having coordinated adjustable nose portions adjacent the top of the fuselage, a sub-plane and parallel airtight pontoons .below the fuselage, a supplemental buoyancy current tube'at each side of the fuselage and longitudinal thereof, a main steering rudder, and

tudinal thereof, a main steering rudder, and

an air compressing device provided with a pilot rudder at the fore part of the machine, said pilot rudder being adapted for simultaneous but reflex movement with respect to the main steering rudder.

30. A flying machine including a main aerofoil with the major dimension lengthwise thereof, a fuselage and surmounted coextensive buoyancy current tube, laterally directed rearwardly declined Wing planes having coordinated adjustable nose portions adjacent the top of the fuselage, a sub-plane and parallel airtight pontoons below the fuselage, a supplemental buoyancy current tube at each side of the fuselage and longi-' tudinal thereof, elevating rudders on the main aerofoil, means whereby said rudders are simultaneously operated, steering rudder, and a coordinated pilot rudder at the fore part of the machine.

81. A flying machine including a main aerofoil with the major dimension lengtlv. wise thereof, a fuselage and surmounted' co extensive buoyancy current tube, laterally directed rearwardly declined wing planes having coordinated adjust-able nose portions adjacent th top of the fuselage, a sub-plane and parallel airtight pontoons below the fuselag-e, a supplemental buoyancy current tube at each side of the fuselage and longitudia main.

nal thereof, elevating rudders on the main aerofoil, means whereby said rudders are simultaneouslyoperated, a main steering rudder, and a coordinated pilot rudder-at the fore part of the machine, said pilot rudder being adapted for simultaneous but reiiex deflection relative to the main steering rudder.

A. flying machine including a main. aerofoil with the major dimension lengthwise thereof, a fuselage and surmounted coextensive buoyancy current tube, laterally directed rearwardly declined wing planes having coordinated adjustable nose portions adjacent the top of the fuselage, a sub-plane and parallel airtight pontoons below the fuselage, a supplemental buoyancy current 1 tube at each side of the fuselage and longitudinal thereof, elevatingrudders on the main aerofoil, means whereby said rudders are simultaneously operated, a main steerins" rudder, and a coordinated pilot rudder fore part of the machine, a main steeriiig rudder, an air compressing tube and associated pilot rudder at the upper fore part of the machine, and n'iechanisin reversely coordin movement ofthe main and pilot rudders.

3 3, .At flying machine including a main aerofoil with the major dimension length wise thereof, a fuselage surmounted CU; extensive buoyancy current tube, laterally directed rearwardly declined wing planes having coordinated adjustable nose portions adjacent the top of the fuselage, a sub-plane and parallel airtight vpontoons below the fuselage, a supplemental buoyancy current tube at each side of the fuselage and longi tudinal thereof, draught and drive propeh 'lers at the fore and after ends of the machine in direct axial alignment, and means for revolving said propellers. I

34:.A flying machine including a main aerofoil with the major dimension lengthwise thereof, a fuselage and surmounted coextensive, buoyancy current tube, laterally directed rearwar'dly declined wing planes having coordinated adjustable nose portions adjacent the top of thefuselage, a sub-plane and parallel airtight pontoons below the fuselage, a supplemental buoyancy current tube at each side of the fusela e and longi tudinal thereof, draught and rive propellers at the fore and after ends of the ma chine in direct alignment above the keel line thereof, and means for driving said propellers.

35. A flying machine including a main aerofoil with the major dimension lengthwise thereof, a fuselage and surmounted cotill Mid

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fuselage, a supplemental buoyancy current tube at each side of the fuselage and longitudinal thereof, draught and drive propellers at the fore and after-ends of the ma chine in direct alignment above the keel line thereof, landing wheels and marine propellers associated with the ontoons, a source of rotative power for each propeller aforesaid, and meansfor coordinating operation of the landingwheels and marine propellers to aid ascent and provide for hydro-navigation respectively.

36. A flying machine including a main aerofoil with the major dimension lengthwisethereof, a fuselage and surmounted coextensive buoyancy current tube, laterally directed rearwardl declined 1 win lanes y 2: having coordinated ad ustable nose portions adjacent the top of the fuselage, a sub plane and parallel airtight pontoon's below the fuselage, a supplemental buoyancy current tube at each side of the fuselage and longitudinal thereof, draught and drive propellers at the fore and after ends of the machine in direct alignment above the keel sourceof rotative power for each propeller aforesaid, and clutching mechanism coordimeme? fuselage, a supplemental buoyancy current tube at each side of the fuselage and longitudinal thereof, lateral stabilizer wings for the machine, means whereby said wings may be automatically or manually controlled to maintain the machine in equilibrium, landing wheels and marine'propellers associated with the pontoons, a source of ro tative power for each propeller aforesaid,

and means for coordinating operation of the landing wheels and marine propellers to aid ascent and provide for hydro-navigatlon res ectively.

'igned at Philadelphia, in the county of -Philadelphia and State of Pennsylvania, the

4th day of August, 1924a J G- DAYNIX; 

